Aeroplane wing rib



March 4, 1930. c. J. MARsToN ET AL 1,749,293

AEROPLANE WING RIB Filed July 24, 1,929

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Patented l Mar. 4, v1930 Y UNITED ySTATI-:s l PATENT foi-"Fics oALnB .1. msi-N .mn-PERLEN w.- onDwAY, or LounoN, Nnwl'nmsnmn AEROPLANE WING nn;

'j applicati@ mea July 24,

Thisr invention relates to new and useful improvements in aircraft' structural details,

and more particularly to a novel wing' rib structure. f A

The primary object of thisinvention is to provide a wing rib structure which will possess considerably moreresistance against strain and stress than rib structures of thev samelightness and of the proportionate size now being employed.

Other lmportant objects and advantages ...of theI inventionwill become more apparent to the reader after considering the invention as described and claimed hereinafter.

In the drawings:

vFigure 1 represents a side elevation of the novel rib construction. Figure 2v represents an enlarged fragmentary' top plan view of the rib.

Figure 3 is an enlarged Afragmentary sectional view taken substantially-on line 3 3 of Figure 1.

Figure 4 represents an enlarged fragmentary sectional view taken substantially on line l.lf-4 of Figure 1.

`Referring to the drawings wherein like numerals designatel like parts, it will vbe seen that thenovel rib construction includes upper and lower longitudinal members 5 and 6 re-4 spective'ly. Each of these longitudinal members yincludes a pair of rails 7-7. The forward ends of the 'rails 7--7 of each longitudinal member are secured to the corres onding end of the connector 8 and the adjacent end portions of the lon itudinal members are disposed against the e ge portions of the reinforcing rame 9 and secured to a suitable element 10. The remaining ends of the longitudinal members (that is the rear end) are secured together as at 11, while a plate 12 is .interposed between the upper and lower s longitudinal members -adj acent their rear f ends and Iprovided with an opening .13 for receiving the usual spars.

' The rails 7 7 of each longitudinal member are spaced apart by the laminated blocks 14 and interposed between the longitudinal members .are the compression bars 15. The opposite ends of the compression bars are reduced as at 16 for disposition between the tion along the upper 1929. serial No. 380,637.l

spaced rails of the longitudinal members and the compression bars are retained'in position by drivin a suitable element 17 transversely through t e rails and the reduced ends 16 of the compression bars. Thus the compression bars are retained in the vertical position shown in Figure 1.

Diagonally disposed tensioning braces 18 are arranged between the adjacent compression members 1'5 and have` their ends interposed bet'ween the rails of the longitudinal members 5 and 6. rihe ends of the bracev members are disposed between the rails 7-7 as in the manner shown in Figure 4, and thus maintained by a suitable pivot element 19.

. It will thus be seen that any load applied to the underside of the 'rib is carried through the compression bars upwardly for disposilongitudinal' member and strain applied in various other quarters will be distributed throughout other corresponding. parts of the structure. A While the foregoing description sets forth the invention in detail, it is to be understood that various 'changes in thel specific shape, size and materials may 'be'resorted to without departingA from the spirit and scope of the invention as claimed hereinafter.

Having thus described the invention, what is claimed as new is:

An aeroplane wing rib of the character described comprising a pair of'longitudinal members connected at their ends and being vertically v.spaced apart at v their intermediacies, and transversely disposed'strengthenn ing bars'interposed betweenthe said longitudinal members,`each of said longitudinal members comprising a pair of spaced parallel rails, longitudinally spaced blocks secured 'between the rails at points intermediate the no strengthening bars for spacing the rails a predetermined distance apart, pairs of -crossed bracing members arranged diagof nally between the said strengthening bars with their end portions interposed and secured between the rails of the longitudinal members adjacent 'the opposite sides of the end portions of the strengthening bars, said strengthening bars being reduced at their l ends to provide extensions for disposition between the said rails and laminated plates having their upper and lower marginal portions interposed between the upper and lower pairs of rails at the opposite end portions 5 thereof, and secured therebetween.

In testimony whereof We aix our signatures.

CALEB J. MARSTON. PERLEY W. ORDVAY. 

